WO2004029415A1 - Dispositif de guidage de fluide de perturbation de vortex thermotolerant - Google Patents

Dispositif de guidage de fluide de perturbation de vortex thermotolerant Download PDF

Info

Publication number
WO2004029415A1
WO2004029415A1 PCT/US2003/014851 US0314851W WO2004029415A1 WO 2004029415 A1 WO2004029415 A1 WO 2004029415A1 US 0314851 W US0314851 W US 0314851W WO 2004029415 A1 WO2004029415 A1 WO 2004029415A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling
vortex
fluid
guide component
leading edge
Prior art date
Application number
PCT/US2003/014851
Other languages
English (en)
Inventor
Alexander Ralph Beeck
Original Assignee
Siemens Westinghouse Power Corporation
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Westinghouse Power Corporation filed Critical Siemens Westinghouse Power Corporation
Priority to EP03728837.0A priority Critical patent/EP1543218B1/fr
Priority to JP2004539779A priority patent/JP4242344B2/ja
Publication of WO2004029415A1 publication Critical patent/WO2004029415A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/10—Influencing flow of fluids around bodies of solid material
    • F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • This invention relates generally to the field of turbine engines and, more particularly, to a fluid guide component having heat-tolerant, vortex-disrupting features.
  • Combustion engines are machines that convert chemical energy stored in fuel into mechanical energy useful for generating electricity, producing thrust, or otherwise doing work. These engines typically include several cooperative sections that contribute in some way to this energy conversion process.
  • air discharged from a compressor section and fuel introduced from a fuel supply are mixed together and burned in a combustion section.
  • the products of combustion also referred to as a "working fluid"
  • the products of combustion are harnessed and directed through a turbine section, where they expand and turn a central rotor shaft. Spinning of the rotor shaft produces torque output, and the rotor shaft output may, in turn, be linked to devices such as an electric generator to produce electricity.
  • Horseshoe vortices typically occur in regions where fluid flows past regions in which upstanding components intersect substantially- planar bodies. As is known in the art, they are caused by a boundary layer roll up. In the gas turbine setting, this type of flow interferes with the transfer of energy from the products of combustion to the engine blades and vanes, thereby reducing the amount of rotor spin and rate of associated electricity generation. Horseshoe vortices also interfere with the manner in which products of combustion flow across the engine fluid-guiding components, producing detrimental variations in fluid exit angles and unwanted flow departure properties, further reducing the effectiveness of downstream blades and vanes. Horseshoe vortices also impact the effectiveness of turbine cooling arrangements by increasing the effective cooling temperature of external-surface-cooling fluids, as a result of unwanted mixing between the relatively-hot working fluid and relatively-cool cooling fluids.
  • the horseshoe vortex phenomenon is not isolated to gas turbine engines; it occurs in a variety of other settings, including near underwater bridge pilings, along control surfaces on submarines and airplanes, and even around various portions of trailers used in the trucking industry. Accordingly, a variety of approaches have been employed to address this issue. For example, to reduce detrimental "scouring" near underwater bridge support pilings, winged deflection devices may be placed upstream of the piling to direct the water flow outwardly, away from the piling. An example of this approach is shown in United States Patent 6,186,445. A different approach is shown in United States Patent 6,283,713, in which airfoil members are shaped with a variety of contours chosen to modify the flow across the members.
  • the device should be cooled in an active, customizable manner and should provide supplemental cooling for key locations, without requiring performance-reducing increases in cooling fluid flow.
  • the device should also be modifiable to ensure appropriate vortex disruption and cooling performance within each turbine stage.
  • the instant invention is a vortex-reducing fluid guide component that includes a base portion and an upstanding body portion.
  • An internally-cooled blending element extends between the base portion and a leading edge of the body portion.
  • the blending element includes a deflection region that advantageously interferes with horseshoe vortex formation.
  • the blending element directs cooling fluid into a supplemental cooling channel disposed between the blending element and the intersection of the body portion leading edge and the base portion.
  • the supplemental cooling channel captures cooling fluid used to cool the blending member and synergistically provides additional cooling to the body portion leading edge/base interface.
  • the channel is customizable to provide selected amounts of residual cooling downstream of the channel.
  • the component includes a strategically-perforated impingement panel or member that distributes cooling fluid to selected portions of the blending member, thereby ensuring that key regions within the blending member are efficiently cooled in accordance with temperature distribution.
  • FIG. 1 is a side sectional view of a combustion engine employing the fluid guide component of the present invention
  • FIG. 2 is an isometric view of the fluid guide of the present invention
  • FIG. 3 is a side sectional view of the fluid guide shown in FIG. 2, taken along cutting line III - III';
  • FIG. 4 is a side sectional view of an alternate embodiment of the fluid guide of the present invention.
  • the vortex- reducing fluid guide component 10 of the present invention includes a base portion 12 and a body portion 14, with the body portion extending outward from the base portion.
  • a blending element 16 extends at least partially between the base portion 12 and a leading edge 18 of the body portion 14.
  • the blending element 16 advantageously disrupts, as will be described more fully below, horseshoe vortex formation along the leading edge 18 of the body portion 14.
  • the base portion 12 also includes a cooling fluid conduit 20 that allows cooling fluid 22 to pass through the base portion to contact the blending element 16.
  • the blending element 16 is preferably hollow and has an interior passageway 50 bounded by an interior surface 66.
  • cooling fluid 22 passes through the cooling fluid conduit 20, flows into the blending element interior passageway 50, and travels out through a blending element exit port 24.
  • cooling fluid 22 passing through the interior passageway 50 lowers the temperature of the blending element 16 and helps protect the blending element against thermal damage from the high-temperature products of combustion 26 which flow from an upstream combustion section 68 and across the component 10.
  • the blending element 16 is spaced away from the body portion leading edge 18 to form a supplemental cooling channel 52 along the intersection 29 of the leading edge 18 and the base portion 12.
  • the present invention 10 provides a fluid guiding component having features that reduce horseshoe vortex formation tendencies and which are especially heat tolerant.
  • the present invention 10 also provides enhanced cooling of the body portion/base portion interface 28, especially along the leading edge/base portion 29 of the interface, without requiring performance-impacting increases in cooling fluid flow.
  • the vortex-reducing fluid guide component 10 of the present invention will now be described in detail.
  • the fluid guide component 10 of the present invention is shown in use within an industrial gas turbine engine 30.
  • the fluid guide component 10 includes a body portion 14 that extends radially outward from an associated base portion 12.
  • the base portion 12 and body portion 14 may be integral or formed separately. With either arrangement, the body portion 14 and base portion 12 intersect along a body portion/base interface 28.
  • the body portion/base interface 28 is an area of high stress concentration. As such, this region is characterized by a fillet-type connection which helps, among other things, to transfer loads between the body portion 14 and base portion 12, while inhibiting the formation of cracks.
  • the body portion 14 is an airfoil- shaped stator vane. It is noted, however, that the body portion could be part of a rotating blade (not shown), as well.
  • the body portion 14 includes a leading edge 18 and an opposite trailing edge 32; the body portion is further characterized by a concave pressure side 34 and a suction side 36, which is convex.
  • the body portion 14 is internally cooled, and has an internal cooling chamber 38, with cooling fluid exits 54 that pass through the body portion at key locations, including the leading edge 18, trailing edge 32, and sides 34,36.
  • the internal cooling chamber 38 is in fluid connection with a source of cooling fluid 22, such as discharge air supplied by an upstream compressor section 40, shown in Figure 1. It is noted that other suitable, non-airfoil shapes may also be used, and that internal cooling of the body member 14 is not required.
  • the base portion 12 of the present invention is a mounting shroud which secures the body portion 14 within the turbine section 44 of an associated engine 30.
  • any number of other mounting platforms may be used, including hub portions, casing sections, diffuser struts portions, and swirler vanes in burners.
  • a blending element 16 extends from the base portion 12, toward the body portion leading edge 18.
  • the blending element 16 may be formed separate from the base and body portions 12,14, or may be formed integral with either, or both of them. In the present embodiment, the blending element 14 is formed integral with the base portion 12.
  • a cooling fluid conduit 20 disposed within the base portion 12 allows cooling fluid 22 to pass through the base portion and into the blending member interior passageway 50, thereby reducing the temperature of the blending element 16.
  • the cooling fluid 22 may be air discharged from a compressor section 40.
  • other sources of cooling fluid 22, such as a pump (not shown) may be used if desired.
  • cooling fluid may pass directly into the cooling channel 52 through auxiliary base portion conduits 20' which extend through the base portion 12 but not the cooling chamber 38.
  • the auxiliary base portion conduits 20' may be oriented normal to the base portion 12 or may pitched to impart desired flow properties to the fluid passing therethrough.
  • the blending element 16 resembles a contoured or ramped structure.
  • the blending element 16 is characterized by a deflecting portion 44 that interacts with the working fluid flowing toward the leading edge/base portion interface 29, providing localized flow acceleration and preventing nearwall fluid flow from travelling upstream and rolling up to form a horseshoe vortex.
  • the blending element 16 can be cast or can be formed from several pieces.
  • the deflecting portion 44 is substantially linear, and forms an angle 0 with respect to the base portion. Angle 0 is preferably about 40 degrees, but may range from about 15 degrees to about 60 degrees.
  • the blending element 16 is a single piece, but as noted above, may be formed from more than one piece if desired.
  • the deflection region 44 need not be linear and can have contours chosen to further enhance the vortex-disruption properties of the blending element 16 of the present invention.
  • the deflection region 44 may include curved regions in combination with linear regions, and may include curved regions only.
  • the blending element 16 may be characterized by fillets having "sharp" or pointed regions aligned with stagnation flow.
  • the blending element 16 may also be characterized by more-rounded fillets, with vortex size being proportional to fillet radius.
  • the present invention advantageously reduces the tendency for formation of horseshoe vortices typically associated with fluid flow at intersections of flat surfaces and upstanding members, such as the leading edge/base interface 29. Reducing the magnitude of this type of flow phenomenon results in less disturbed flow along the component 10 and increases the amount of energy which is extracted from the products of combustion 48. Reducing the magnitude of horseshoe vortices also increases the efficiency with which the component is cooled, by reducing unwanted mixing between the products of combustion 48 and cooling fluid flowing over the component 10.
  • a strategically-perforated impingement plate 60 may be included within the blending element interior passageway 50 to guide cooling fluid within the passageway.
  • various portions of the blending element 16 may be cooled in accordance with temperature distribution, ensuring that especially-hot regions (such as upstream areas 62) are cooled effectively, while reducing the amount of cooling fluid directed to less-hot regions (such as downstream areas 64).
  • the blending element 16 is cooled effectively and efficiently, without wastefully diverting cooling fluid to regions that have minimal cooling requirements.
  • the blending element 16 also includes a bracing region 46.
  • the bracing region 46 includes at least one cooling fluid exit or port 24 that allows cooling fluid 22 to pass out of the region 50 bounded by the blending element 16.
  • the bracing region 46 is spaced apart from the leading edge 18 of the body portion 14, thereby forming a supplemental cooling channel 52 into which cooling fluid 22 exiting the cooling fluid port 24 will flow.
  • the bracing region 46 has a substantially-triangular cross section, but may be modified to impart a variety of flow characteristics.
  • the cooling channel 52 may include tapers or curves that will modify the flow dynamics of the channel: narrowing the channel 52 in the direction of downstream cooling fluid flow will increase the velocity of cooling fluid 22 within the channel, while broadening the channel in the same direction will decrease the velocity of the cooling fluid in the channel.
  • the number of exit ports 24 and the mean distance D m between the bracing region and the leading edge may each be selected in accordance with these considerations, as well. An appropriate range would be about 5% to 50% of the leading edge diameter.
  • the channel 52 may be tapered with regard to a radial ⁇ i.e., away from and toward the base portion 12) axis, with regard to a longitudinal ⁇ i.e., generally along the base portion) axis, and with regard to spacing relative to the contours of the leading edge portion 18.
  • this arrangement allows strategic selection of these attributes to provide a great deal of flexibility regarding the amount of supplemental cooling which the channel 52 provides, as well as the amount of cooling capacity that remains in the cooling fluid 22 for residual cooling of the body portion sides 34,36, as the fluid leaves the channel.
  • the present invention is not limited to use with industrial gas turbine engines, as it is useful in all manner of turbine engines, including aero-derivative engines, as well.
  • the flow of products of combustion, which produces electricity, and the flow of cooling fluid, which beneficially lowers the component temperature, are both enhanced by the blending element 16 of the present invention.
  • the blending element 16 of the present invention improves the quality of flow across the component of the present invention 10.
  • the blending element 16 reduces the energy of the flow which is used to drive the horseshoe vortex along the sides 34,36 of the body member, allowing energy to be transferred to the body portion with reduced losses and increased effectiveness.
  • the present fluid guide component 10 incorporates features that to not only actively cool the blending element 16, but which also provide supplemental cooling for the highly-stressed body leading edge/base interface region 29 without requiring additional flows of cooling fluid 22.
  • a supplemental cooling channel 52 which cooperates with the blending element 16 to recover cooling fluid 22 for cooling the area adjacent the leading edge/base portion 29 interface, the cooling arrangement of the present invention 10 provides a combination of features that synergistically provide increased performance and enhanced cooling efficiency.
  • the blending element 16' may be a discrete component formed from a ceramic or other heat-resistant material, such that internal cooling is not needed.
  • the component 10' still disrupts horseshoe vortex formation and provides a supplemental cooling channel 52. Cooling fluid entering the supplemental cooling channel 52 through a dedicated cooling channel fluid port 74 disposed within the leading edge 28 of the body member 16, adjacent the body portion leading edge/base portion interface 29. With this arrangement, cooling fluid 22 still enters the supplemental cooling channel 52, and the performance of the channel is modifiable in accordance with the residence times and residual cooling considerations discussed above.
  • the blending element 16' is a single-piece construction, but may be formed from more than one piece if desired.
  • the blending element 16' is a contoured plug held in place with respect to the base and body portions 12,14 via a tongue-and- groove type arrangement.
  • a biasing member 72 such as a spring, may be included to dampen the blending element 16' fixing arrangement, advantageously allowing the blending element to tolerate vibration and thermal expansion within the component 10 during operation.
  • the present invention 10,10' provides a combination of features that simultaneously provide reduced vortex-forming tendencies and a unique, extremely- efficient cooling arrangement, resulting in a fluid guide component 10 that achieves improved aerodynamic and power extraction properties, without requiring performance-degrading cooling fluid flow increases.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un dispositif de guidage de fluide permettant de diminuer le vortex (10). Ce dispositif de guidage de fluide comprend une partie de base (12) et une partie de corps érigée (14). Un élément de mélange refroidi internement (16) s'étend entre la partie de base et un bord d'attaque (18) de la partie de corps. Cet élément de mélange comprend une zone de déflexion qui interrompt, de manière avantageuse, la formation de vortex en fer à cheval. Ce dispositif de guidage de fluide comprend un canal de refroidissement supplémentaire entre l'élément de mélange et l'intersection du bord d'attaque de la partie de corps et de la partie de base. Dans un mode de réalisation, le canal de refroidissement supplémentaire (52) permet de capturer le liquide de refroidissement utilisé pour refroidir l'élément de mélange et d'engendrer un refroidissement supplémentaire au niveau de l'interface de base/du bord d'attaque de la partie du corps. Ce composant comporte un élément ou un panneau d'impact perforé à des emplacements stratégiques (60) qui permet de distribuer le liquide de refroidissement à des parties sélectionnées de l'élément de mélange, ce qui garantit que des zones clés au sein de l'élément de mélange sont efficacement refroidies en fonction de la distribution thermique.
PCT/US2003/014851 2002-09-26 2003-05-12 Dispositif de guidage de fluide de perturbation de vortex thermotolerant WO2004029415A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP03728837.0A EP1543218B1 (fr) 2002-09-26 2003-05-12 Dispositif de guidage de fluide de perturbation de vortex thermotolerant
JP2004539779A JP4242344B2 (ja) 2002-09-26 2003-05-12 渦を破壊する熱耐性流体案内コード

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/255,893 US6884029B2 (en) 2002-09-26 2002-09-26 Heat-tolerated vortex-disrupting fluid guide component
US10/255,893 2002-09-26

Publications (1)

Publication Number Publication Date
WO2004029415A1 true WO2004029415A1 (fr) 2004-04-08

Family

ID=32041758

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2003/014851 WO2004029415A1 (fr) 2002-09-26 2003-05-12 Dispositif de guidage de fluide de perturbation de vortex thermotolerant

Country Status (5)

Country Link
US (1) US6884029B2 (fr)
EP (1) EP1543218B1 (fr)
JP (1) JP4242344B2 (fr)
KR (1) KR100712142B1 (fr)
WO (1) WO2004029415A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1688586A1 (fr) * 2003-10-31 2006-08-09 Kabushiki Kaisha Toshiba Structure de grille d'aubes de turbine
EP1847682A1 (fr) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Méthode d'alimentation d'un fluide dans le flux principal de gaz d'une turbine et aube de turbine associée.
EP1936117A3 (fr) * 2006-12-15 2009-05-13 General Electric Company Aube avec générateur de plasma au bord d'attaque pour reduire les vortex et procédé de fonctionnement associé
EP2083168A3 (fr) * 2008-01-16 2013-01-09 Hitachi Mitsubishi Hydro Corporation Tube d'aspiration dans une machine hydraulique

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2401915B (en) * 2003-05-23 2006-06-14 Rolls Royce Plc Turbine blade
US20060032233A1 (en) * 2004-08-10 2006-02-16 Zhang Luzeng J Inlet film cooling of turbine end wall of a gas turbine engine
DE102004054752A1 (de) * 2004-11-12 2006-05-18 Rolls-Royce Deutschland Ltd & Co Kg Schaufel einer Strömungsarbeitsmaschine mit erweiterter Randprofiltiefe
US7217096B2 (en) * 2004-12-13 2007-05-15 General Electric Company Fillet energized turbine stage
US7841828B2 (en) * 2006-10-05 2010-11-30 Siemens Energy, Inc. Turbine airfoil with submerged endwall cooling channel
FR2927356B1 (fr) * 2008-02-07 2013-03-01 Snecma Aubes pour roue a aubes de turbomachine avec rainure pour le refroidissement.
GB0808206D0 (en) * 2008-05-07 2008-06-11 Rolls Royce Plc A blade arrangement
US8105037B2 (en) * 2009-04-06 2012-01-31 United Technologies Corporation Endwall with leading-edge hump
EP2248996B1 (fr) * 2009-05-04 2014-01-01 Alstom Technology Ltd Turbine à gaz
DE102009052142B3 (de) * 2009-11-06 2011-07-14 MTU Aero Engines GmbH, 80995 Axialverdichter
US8668454B2 (en) * 2010-03-03 2014-03-11 Siemens Energy, Inc. Turbine airfoil fillet cooling system
US20130081407A1 (en) * 2011-10-04 2013-04-04 David J. Wiebe Aero-derivative gas turbine engine with an advanced transition duct combustion assembly
CH705838A1 (de) * 2011-12-05 2013-06-14 Alstom Technology Ltd Abgasgehäuse für eine Gasturbine sowie Gasturbine mit einem Abgasgehäuse.
DE102012207735B4 (de) * 2012-05-09 2024-08-22 Man Energy Solutions Se Schaufelgitter einer Strömungsmaschine
US9644483B2 (en) * 2013-03-01 2017-05-09 General Electric Company Turbomachine bucket having flow interrupter and related turbomachine
DE102013206207A1 (de) * 2013-04-09 2014-10-09 MTU Aero Engines AG Schaufelblatt für eine Strömungsmaschine mit Hinterkantenprofilierung, Schaufel und integral beschaufelter Rotor
US10132498B2 (en) 2015-01-20 2018-11-20 United Technologies Corporation Thermal barrier coating of a combustor dilution hole
US11118466B2 (en) * 2018-10-19 2021-09-14 Pratt & Whiiney Canada Corp. Compressor stator with leading edge fillet

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2984454A (en) * 1957-08-22 1961-05-16 United Aircraft Corp Stator units
US3314648A (en) * 1961-12-19 1967-04-18 Gen Electric Stator vane assembly
US4208167A (en) * 1977-09-26 1980-06-17 Hitachi, Ltd. Blade lattice structure for axial fluid machine
US4739621A (en) * 1984-10-11 1988-04-26 United Technologies Corporation Cooling scheme for combustor vane interface
GB2233401A (en) * 1989-06-21 1991-01-09 Rolls Royce Plc Improvements in or relating to gas turbine engines
US5609466A (en) * 1994-11-10 1997-03-11 Westinghouse Electric Corporation Gas turbine vane with a cooled inner shroud
US5772398A (en) * 1996-01-04 1998-06-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Cooled turbine guide vane
EP1197636A2 (fr) * 2000-10-12 2002-04-17 ROLLS-ROYCE plc Refroidissement des aubes des turbines à gaz
US6419446B1 (en) * 1999-08-05 2002-07-16 United Technologies Corporation Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3697120A (en) 1969-11-03 1972-10-10 Walter Selden Saunders Drag reducer for land vehicles
JPH09324604A (ja) * 1996-06-06 1997-12-16 Mitsubishi Heavy Ind Ltd 軸流タービンの翼列
GB2333401A (en) 1998-01-14 1999-07-21 Cherry Electrical Prod Paper membrane for use in a membrane circuit
WO1999044887A1 (fr) 1998-03-06 1999-09-10 Batcho Paul F Procede et appareil d'attenuation des ecoulements aux jonctions
US6099251A (en) * 1998-07-06 2000-08-08 United Technologies Corporation Coolable airfoil for a gas turbine engine
GB9823840D0 (en) 1998-10-30 1998-12-23 Rolls Royce Plc Bladed ducting for turbomachinery

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2984454A (en) * 1957-08-22 1961-05-16 United Aircraft Corp Stator units
US3314648A (en) * 1961-12-19 1967-04-18 Gen Electric Stator vane assembly
US4208167A (en) * 1977-09-26 1980-06-17 Hitachi, Ltd. Blade lattice structure for axial fluid machine
US4739621A (en) * 1984-10-11 1988-04-26 United Technologies Corporation Cooling scheme for combustor vane interface
GB2233401A (en) * 1989-06-21 1991-01-09 Rolls Royce Plc Improvements in or relating to gas turbine engines
US5609466A (en) * 1994-11-10 1997-03-11 Westinghouse Electric Corporation Gas turbine vane with a cooled inner shroud
US5772398A (en) * 1996-01-04 1998-06-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Cooled turbine guide vane
US6419446B1 (en) * 1999-08-05 2002-07-16 United Technologies Corporation Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine
EP1197636A2 (fr) * 2000-10-12 2002-04-17 ROLLS-ROYCE plc Refroidissement des aubes des turbines à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1688586A1 (fr) * 2003-10-31 2006-08-09 Kabushiki Kaisha Toshiba Structure de grille d'aubes de turbine
EP1688586A4 (fr) * 2003-10-31 2011-11-02 Toshiba Kk Structure de grille d'aubes de turbine
EP1847682A1 (fr) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Méthode d'alimentation d'un fluide dans le flux principal de gaz d'une turbine et aube de turbine associée.
EP1936117A3 (fr) * 2006-12-15 2009-05-13 General Electric Company Aube avec générateur de plasma au bord d'attaque pour reduire les vortex et procédé de fonctionnement associé
EP2083168A3 (fr) * 2008-01-16 2013-01-09 Hitachi Mitsubishi Hydro Corporation Tube d'aspiration dans une machine hydraulique

Also Published As

Publication number Publication date
US20040179943A1 (en) 2004-09-16
KR100712142B1 (ko) 2007-04-27
JP2006500511A (ja) 2006-01-05
KR20050057588A (ko) 2005-06-16
EP1543218A1 (fr) 2005-06-22
US6884029B2 (en) 2005-04-26
JP4242344B2 (ja) 2009-03-25
EP1543218B1 (fr) 2013-07-31

Similar Documents

Publication Publication Date Title
US6884029B2 (en) Heat-tolerated vortex-disrupting fluid guide component
US20190106992A1 (en) Gas turbine engines with improved leading edge airfoil cooling
US6607355B2 (en) Turbine airfoil with enhanced heat transfer
EP2815078B1 (fr) Composant de moteur à turbine à gaz et agencement associé de chambre de combustion
EP2815107B1 (fr) Composant de moteur à turbine à gaz et procédé associé de production d'un trou de refroidissement
US8572983B2 (en) Gas turbine engine component with impingement and diffusive cooling
EP2815097B1 (fr) Composant pour un moteur à turbine à gaz et procédé associé pour produire un trou de refroidissement dans une paroi de moteur à turbine à gaz
EP2855853B1 (fr) Profil d'aube
US20090304494A1 (en) Counter-vortex paired film cooling hole design
WO2017020178A1 (fr) Agencements de refroidissement dans des aubes de turbine
EP3483395B1 (fr) Conduits inter-turbine comportant des mécanismes de régulation d'écoulement
CA2923279A1 (fr) Composante de moteur
EP2634370B1 (fr) Aube de turbine avec cavité de noyau ayant un virage profilé
JP2015224634A (ja) ロータブレードクーラント流
US20200378262A1 (en) Gas turbine engines with improved airfoil dust removal
EP3453831B1 (fr) Aube comportant des socles profilés
US11230931B1 (en) Inserts for airfoils of gas turbine engines
EP4023855B1 (fr) Aube de rotor refroidie
US11629601B2 (en) Turbomachine rotor blade with a cooling circuit having an offset rib

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): JP KR

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PT RO SE SI SK TR

121 Ep: the epo has been informed by wipo that ep was designated in this application
WWE Wipo information: entry into national phase

Ref document number: 2003728837

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 1020057005245

Country of ref document: KR

WWE Wipo information: entry into national phase

Ref document number: 2004539779

Country of ref document: JP

WWP Wipo information: published in national office

Ref document number: 1020057005245

Country of ref document: KR

WWP Wipo information: published in national office

Ref document number: 2003728837

Country of ref document: EP